Passive mechanical isolation is often times the first step taken to remedy vibration issues on-board a spacecraft. In many
cases, this is done with a hexapod of axial members or struts to obtain the desired passive isolation in all six degrees-of-freedom
(DOF). In some instances, where the disturbance sources are excessive or the payload is particularly sensitive
to vibration, additional steps are taken to improve the performance beyond that of passive isolation. Additional
performance or functionality can be obtained with the addition of active control, using a hexapod of hybrid
(passive/active) elements at the interface between the payload and the bus. This paper describes Honeywell's Isolation,
Pointing, and Suppression (IPS) system. It is a hybrid isolation system designed to isolate a sensitive spacecraft payload
with very low passive resonant break frequencies while affording agile independent payload pointing, on-board payload
disturbance rejection, and active isolation augmentation. This system is an extension of the work done on Honeywell's
previous Vibration Isolation, Steering, and Suppression (VISS) flight experiment. Besides being designed for a different
size payload than VISS, the IPS strut includes a dual-stage voice coil design for improved dynamic range as well as
improved low-noise drive electronics. In addition, the IPS struts include integral load cells, gap sensors, and payloadside
accelerometers for control and telemetry purposes. The associated system-level control architecture to accomplish
these tasks is also new for this program as compared to VISS. A summary of the IPS system, including analysis and
hardware design, build, and single axis bipod testing will be reviewed.